$3.$ For the given pressure ratio $\backslash ($ p$\_\{0\}/$ p$\_\{1\}\backslash ),$ assuming isentropic expansion in the nozzle and a frozen reaction $($not$-$changing gas properties, such as molar mass, ratio of specific heats, composition$),$ calculate the nozzle exit temperature. We are analyzing a solid rocket motor $($aluminized ammonium perchlorate composite, chamber pressure $1000$ psia$),$ using an internal burning tube design. Use Table $5-7.$ TABLE $5-7.$ Variation of Calculated Performance Parameters for an Aluminized Ammonium Perchlorate Composite Propellant as a Function of Chamber Pressure for Expansion to Sea Level $(1$ atm$)$ with Shifting Equilibrium

$\backslash (\{\}^\{\backslash$text $\{$a $\}\}\backslash )$ At optimum expansion.

Source: From Ref. S$-13.$